Titanium-aluminide components

Patent metadata

Field	Value
Publication number	US-2016138423-A1
Application number	US-201414212061-A
Country	US
Kind code	A1
Filing date	Mar 14, 2014
Priority date	Mar 15, 2013
Publication date	May 19, 2016
Grant date	—

Abstract

The present disclosure relates to a hot section gas turbine engine component assembly and a method for forming such.

First claim

What is claimed is:

1 . A case for use in a gas turbine engine comprising a sheet metal skin made from a first material including titanium, the sheet metal skin formed to define a plurality of concave features and to define an internal cavity, and a core made from a second material including titatium and aluminum arranged in the internal cavity and integrally bonded to the sheet metal skin to reinforce the sheet metal skin.

2 . The case of claim 1 , wherein the sheet metal skin includes a first sheet metal portion having a first edge and a second sheet metal portion having a second edge arranged adjacent to the first edge to form a joint therebetween.

3 . The case of claim 2 , wherein joint is sealed by a weld line.

4 . The case of claim 1 , wherein the second material is a gamma titanium-aluminide alloy.

5 . The case of claim 4 , wherein the gamma titanium-aluminide alloy has an aluminum content of about 46 percent by weight.

6 . A component for use in a gas turbine engine comprising
a sheet metal skin made from a first material including titanium, the sheet metal skin formed to define a plurality of concave features and to define an internal cavity, and a core made from a second material including titatium and aluminum arranged in the internal cavity and integrally bonded to the sheet metal skin to reinforce the sheet metal structure.

7 . The component of claim 6 , wherein the sheet metal skin includes a first sheet metal portion having a first edge and a second sheet metal portion having a second edge arranged adjacent to the first edge to form a joint therebetween.

8 . The component of claim 7 , wherein joint is sealed by a weld line.

9 . The component of claim 6 , wherein the second material is a gamma titanium-aluminide alloy.

10 . The component of claim 9 , wherein the gamma titanium-aluminide alloy has an aluminum content of about 46 percent by weight.

11 . The component of claim 6 , wherein the component is manufactured by a process including the steps of (i) filling the internal cavity of the sheet metal skin with a powder metal material, (ii) sealing the internal cavity of the sheet metal skin with the powder metal material inside to form a near-net shaped preform, and (iii) heating the near-net shaped preform to a predetermined temperature at which the powder metal material is sintered to provide the core.

12 . The component of claim 11 , wherein the heating step is performed in a pressurized atmosphere.

13 . The component of claim 11 , wherein the process further includes the step of (iv) drilling holes into the component to form post-processed features.

14 . The component of claim 11 , wherein the process further includes the step of (iv) polishing external surfaces of the component to provide controlled surfaces.

15 . A method comprising the steps of
forming a first portion and a second portion of a titanium alloy sheet metal structure, partially joining the first portion and the second portion of the titanium alloy sheet metal structure, filing the titanium alloy sheet metal structure with a gamma titanium aluminide powder metal, creating a near-net shape perform by sealing the titanium alloy sheet metal structure, and hot isostatic pressing the near-net shape perform to integrally bond the titanium alloy sheet metal structure with the gamma titanium aluminide powder metal.

16 . The component of claim 15 , wherein the method further includes the step of drilling holes into the component to form post-processed features.

17 . The component of claim 15 , wherein the method further includes the step of polishing external surfaces of the component to provide controlled surfaces.

18 . The component of claim 15 , wherein the gamma titanium-aluminide powder has an aluminum content of about 46 percent by weight.

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Ottow Nathan W
• Ress Robert A

Classifications

• B22F1/00

  Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties · CPC title

• B22F3/15 Primary

  Hot isostatic pressing · CPC title

• F05D2230/10

  by removing material · CPC title

• F05D2300/174

  Titanium alloys, e.g. TiAl · CPC title

• C22C14/00

  Alloys based on titanium · CPC title